Gas turbomachine leak detection system and method

Patent metadata

Field	Value
Publication number	US-10989620-B2
Application number	US-201816109057-A
Country	US
Kind code	B2
Filing date	Aug 22, 2018
Priority date	Sep 26, 2017
Publication date	Apr 27, 2021
Grant date	Apr 27, 2021

Abstract

Various embodiments include an offline leak detection system for a turbomachine fuel system. In some embodiments, the leak detection system includes: a fluid supply system fluidly connected to at least one fuel line of the turbomachine, the fluid supply system for delivering a non-flammable fluid to the combustor; a control system operably connected to the fluid supply system, the control system controlling a flow of the non-flammable fluid through the at least one fuel line, and controlling a pressure of the non-flammable fluid in the at least one fuel line to a pressure substantially equal to an operational fuel pressure of the turbomachine; and an optical monitor for determining a presence of the non-flammable fluid on an exterior of the at least one fuel line, the presence of the non-flammable fluid on the exterior of the at least one fuel line indicating a leak.

First claim

What is claimed is:

1. A method of detecting a leak in a fuel system of a turbomachine having at least one combustor including a combustion chamber, the method comprising:
pressurizing a fuel line immediately upstream of the combustion chamber with a non-flammable fluid to a pressure substantially equal to an operational fuel pressure of the turbomachine;
optically monitoring an exterior of the fuel line to determine a presence of the non-flammable fluid at the exterior of the fuel line, the presence of the non-flammable fluid on the exterior of the fuel line indicating a leak; and
delivering the non-flammable fluid to the combustion chamber of the combustor, whereby a drain coupled to the combustor is opened while the non-flammable fluid is being delivered to the combustion chamber, and wherein an exit flow rate of the non-flammable fluid exiting the combustion chamber via the drain is greater than a delivery flow rate of the non-flammable fluid being delivered to the combustion chamber.

2. The method of claim 1 , wherein the pressurizing the fuel line includes pressurizing the fuel line downstream of an end cover assembly of the combustor.

3. The method of claim 1 , wherein the non-flammable fluid is water, and the pressurizing of the fuel line includes pressurizing the fuel line with a water injection system of the turbomachine that is configured to direct water to a compressor of the turbomachine during a wash.

4. The method of claim 1 , further comprising simultaneously supplying atomized air from an atomized air source to the combustor while directing the non-flammable fluid to the combustion chamber.

5. The method of claim 1 , wherein the drain includes a hose connected to the combustor and in fluid communication with the combustion chamber, the hose having a diameter equal to approximately 12 millimeters.

6. The method of claim 1 , wherein the pressurizing includes pressurizing the fuel line with the non-flammable fluid to a pressure greater than or approximately equal to 4.2 Megapascals (MPa).

7. The method of claim 1 , further comprising turning the turbomachine to a speed approximately 10% to approximately 14% of an operating speed of the turbomachine during the pressurizing and the optical monitoring.

8. A leak detection system for a fuel system of a turbomachine having at least one combustor including a combustion chamber, the leak detection system comprising:
a fluid supply system fluidly connected to at least one fuel line of the turbomachine, the fluid supply system for delivering a non-flammable fluid to the combustion chamber of the combustor, wherein a drain is coupled to the combustor and is configured to open in response to the non-flammable fluid is being delivered to the combustion chamber, and wherein the drain is sized to permit the non-flammable fluid to exit the combustion chamber at an exit flow rate that is greater than a delivery flow rate of the non-flammable fluid being delivered to the combustion chamber;
a control system operably connected to the fluid supply system, the control system controlling a flow of the non-flammable fluid through the at least one fuel line, and controlling a pressure of the non-flammable fluid in the at least one fuel line to a pressure substantially equal to an operational fuel pressure of the turbomachine; and
an optical monitoring system for determining a presence of the non-flammable fluid on an exterior of the at least one fuel line, the presence of the non-flammable fluid on the exterior of the at least one fuel line indicating a leak.

9. The leak detection system of claim 8 , wherein the fluid supply system includes a water injection system of the turbomachine that is configured to direct water to a compressor of the turbomachine during a wash.

10. The leak detection system of claim 8 , wherein the at least one fuel line is downstream of an end cover assembly of the combustor.

11. The leak detection system of claim 10 , wherein the at least one fuel line includes a check valve upstream of the combustor, and wherein the at least one fuel line is pressurized from the check valve to the at least one combustor.

12. The leak detection system of claim 10 , wherein the drain includes a hose connected to the combustor and in fluid communication with the combustion chamber, the hose having a diameter equal to approximately 12 millimeters.

13. The leak detection system of claim 8 , wherein the control system is configured to control the pressure of the non-flammable fluid in the at least one fuel line to a pressure greater than or approximately equal to 4.2 Megapascals (MPa).

14. A fuel line leak detection system for a gas turbomachine comprising:
a non-flammable fluid source fluidly connected to a plurality of fuel lines of the turbomachine upstream of a plurality of combustors of the turbomachine, each combustor of the plurality of combustors including a respective combustion chamber, the plurality of fuel lines delivering a non-flammable fluid to the respective combustion chamber of each combustor of the plurality of combustors, wherein each combustor of the plurality of combustors includes a drain in fluid communication with the respective combustion chamber of each combustor of the plurality of combustors, the drain being configured to open in response to the non-flammable fluid being delivered to the respective combustion chamber of each combustor of the plurality of combustors, and wherein the drain is sized to permit the non-flammable fluid to exit the respective combustion chamber of each combustor of the plurality of combustors at an exit flow rate that is greater than a delivery flow rate of non-flammable fluid being delivered to the respective combustion chamber of each combustor of the plurality of combustors;
a multiport valve fluidly connected to the plurality of fuel lines between the non-flammable fluid source and the plurality of combustors, the multiport valve directing the non-flammable fluid to individual ones of the plurality of combustors;
a pressure source fluidly connected to the plurality of fuel lines, the pressure source configured to pressurize the plurality of fuel lines immediately upstream of the combustor with the non-flammable fluid to a pressure substantially equal to an operational fuel pressure of the turbomachine; and
means for determining a presence of the non-flammable fluid on an exterior of the plurality of fuel lines, the presence of the non-flammable fluid on the exterior of the plurality of fuel lines indicating a leak.

15. The fuel line leak detection system of claim 14 , wherein the pressure source includes a pump having a variable frequency drive, the pump configured to maintain the pressure substantially equal to the operational fuel pressure of the turbomachine.

16. The fuel line leak detection system of claim 14 , further comprising a starter connected to a rotor shaft of the turbomachine, the starter turning the rotor shaft to a speed approximately 10% to approximately 14% of an operating speed of the turbomachine while the non-flammable fluid is delivered to the plurality of combustors.

17. The fuel line leak detection system of claim 14 , wherein each drain includes a hose in fluid communication with the respective combustion chamber, the hose having a diameter equal to approximately 12 millimeters.

18. The fuel line leak detection system of claim 14 wherein the drain prevents the non-flammable fluid from collecting in the plurality of combustors.

19. The fuel line leak detection system of claim 14 , wherein the pressure source is co

Assignees

• Gen Electric

Inventors

• Saha Rajarshi
• Aboujaib Mohamad-Maher
• Faqihi Bouria
• Penna Sindhu

Classifications

• G01M3/025 Primary

  Details with respect to the testing of engines or engine parts · CPC title

• G01M3/222 Primary

  for tubes · CPC title

• G01M15/14

  Testing gas-turbine engines or jet-propulsion engines · CPC title

• G01M3/38

  by using light (G01M3/02 takes precedence) · CPC title

• F05D2260/83

  Testing, e.g. methods, components or tools therefor · CPC title